Thermal management system

1. Avionics control assembly, comprising: an engine control device having an avionics housing defining an exterior and an interior, with at least one connector extending from the exterior of the avionics housing and at least one sensor located within the interior; and a heat exchanger having a heat exchanger housing defining a fluid pathway including at least one fluid passageway leading from an inlet port of the heat exchanger to an outlet port of the heat exchanger, the heat exchanger housing have a first side and a second side, opposite the first side where the heat exchanger housing includes at least one aperture extending through the heat exchanger housing from the first side to the second side and where the aperture is fluidly separate from the fluid pathway, where the heat exchanger is operably coupled to the exterior of the avionics housing with the at least one connector located within the aperture and heat from liquid flowing through the fluid pathway is transferred via at least one of conduction or convection to the avionics housing.

2. The avionics control assembly of claim 1 wherein at least a portion of the heat exchanger is spaced from the exterior of the avionics housing and the heat is transferred via both conduction and convection to the avionics housing.

3. The avionics control assembly of claim 2 , further comprising a backing plate mounted to the second side of the heat exchanger housing.

4. The avionics control assembly of claim 3 , further comprising a set of legs with elevated portions extending from the backing plate and spacing the backing plate away from the exterior of the avionics housing.

5. The avionics control assembly of claim 3 wherein the backing plate comprises a planar body with at least one extension protruding from a surface thereof, the at least one extension configured to form an additional thermal pathway to conductively transfer heat from the heat exchanger to the exterior of the avionics housing.

6. The avionics control assembly of claim 3 wherein the backing plate comprise a planar body having a through-passage configured for the at least one connector to pass therethrough.

7. The avionics control assembly of claim 6 , further comprising a bypass heat exchange fluid pathway that connects the inlet port of the heat exchanger to the outlet port, bypassing the heat exchanger and a bypass valve configured to control fluid communication between the inlet port and the heat exchange fluid pathway.

8. The avionics control assembly of claim 2 , further comprising a set of legs with elevated portions extending from the heat exchanger housing and spacing the second side of the heat exchanger away from the exterior of the avionics housing.

9. The avionics control assembly of claim 1 , further comprising a backing plate mounted to the second side of the heat exchanger housing and having a set of legs extending from the backing plate and mounting the heat the heat exchanger to the exterior of the avionics housing.

10. The avionics control assembly of claim 9 wherein a portion of the backing plate extends about a portion of the heat exchanger housing.

11. The avionics control assembly of claim 10 wherein the portion of the backing plate lines the aperture.

12. The avionics control assembly of claim 10 wherein the portion of the backing plate extends along a periphery of the heat exchanger housing.

13. The avionics control assembly of claim 1 , further comprising a valve configured to control fluid communication between the inlet port and the fluid pathway.

14. The avionics control assembly of claim 1 , further comprising a bypass heat exchange fluid pathway that connects the inlet port of the heat exchanger to the outlet port, bypassing the heat exchanger and a bypass valve configured to control fluid communication between the inlet port and the heat exchange fluid pathway.

15. The avionics control assembly of claim 1 , further comprising a heat exchange fluid in the heat exchanger.

16. The avionics control assembly of claim 15 wherein the heat exchange fluid includes oil.

17. The avionics control assembly of claim 1 wherein the engine control device is a full authority digital engine control device or a pressure subsystem engine control device.

18. A method of controlling temperature in an electronics device having an avionics housing, the method comprising: flowing heat exchange fluid from a portion of a turbine engine to a heat exchanger that is operably coupled to an electronics device located within a nacelle of a turbine engine where the heat exchanger includes a heat exchanger housing defining a fluid pathway including at least one fluid passageway leading from an inlet port of the heat exchanger to an outlet port of the heat exchanger, the heat exchanger housing have a first side and a second side, opposite the first side where the heat exchanger housing includes at least one aperture extending through the heat exchanger housing from the first side to the second side and where the aperture is fluidly separate from the fluid pathway, where the heat exchanger is operably coupled to the exterior of the avionics housing with at least one connector of the electronics device located within the aperture; and conveying heat from the flowing heat exchange fluid to an interior of the electronics device via at least one of convection or conduction to at least one of increase a temperature of the electronics device, thaw frozen ice in the electronics device, prevent freezing of water in the electronics device, or evaporate water in the electronics device.

19. The method of claim 18 wherein the heat exchange fluid is engine oil.

20. The method of claim 18 wherein the flowing heat exchange fluid further comprises controlling a bypass of the heat exchange fluid through a bypass fluid pathway.